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Shock Wave and Turbulent Boundary Layer Interaction and Turbulence Phenomena in a Supersonic Rectangular Duct

超音速矩形管内冲击波与湍流边界层相互作用及湍流现象

基本信息

批准号：
09650175
负责人：
SUGUIYAMA Hiromu
金额：
$ 2.37万
依托单位：
MURORAN INSTITUTE OF TECHNOLOGY
依托单位国家：
日本
项目类别：
Grant-in-Aid for Scientific Research (C)
财政年份：
1997
资助国家：
日本
起止时间：
1997 至 1998
项目状态：
已结题

来源：
https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-09650175/
关键词：
Supersonic Flow Shock Wave Supersonic Internal Flow Shock Wave and Boundary Layer Interactionn Compressible Turbulent Boundary Layer Rectangular Duct Pseudo-Shock Wave Scramjet Engine 超音速流れ超音速内部流れ乱流

项目摘要

When a supersonic or hypersonic flow in ducts which could be a flow plug. nozzle or combustion heat release, interacts with downstream blockage devices, a multiple shock wave system is produced as the result of shock wave and duct wall boundary layer interactions. A multiple shock wave system is called as "psendo-shock wave" or "shock train". The study of multiple shock wave and turbulent boundary layer interaction (MSW-TBLI) has important implications for the desigli and operation of scramjet engine/combustor-isolators and supersonic diffusers.In this project, the internal structure and turbulence phenomena of multiple shock wave/ turbulent boundary layer interactions (MSW-TBLI) in a rectangular duct were investigated.First, the internal structure of the MSW-TBLI was observed using schlieren photographs. laser holo-graphic interferograms and surface oil flow pictures. It was found that the boundary layer thickness increases at the leading oblique shock of the bifurcated first shock and decreases behind the trailing shock of the first shock, and that in the low confinenient case, the boundary layer separates under the bifurcated first shock, and in the high confinemeut. case the separation region of the boundary layer becomes small.Next, the time-mean and fluctuating velocities in the MSW-TBLI were measured in detail using the LDV.Spatial distributions of the turbulence intensity. Reynolds shear stress. and turbulence kinetic energy are presented. It was found that the tubulence intensity. Reynolds shear stress and turbulence kinetic energy in the boundary layer of the MSW-TBLI increases under the bifurcated first shock

当管道中出现超音速或高超音速流动时，可能会出现流动堵塞。喷嘴或燃烧放热与下游阻塞装置相互作用，由于激波和管道壁边界层相互作用，产生了多激波系统。多重冲击波系统被称为“伪冲击波”或“冲击串”。多激波与湍流边界层相互作用的研究多激波/湍流边界层相互作用（MSW-TBLI）的研究对超燃冲压发动机/燃烧室隔离段和超声速扩压器的设计和运行具有重要意义首先，利用纹影照片观察了矩形管道内微重力TBLI的内部结构。激光全息干涉图和表面油流图。结果表明，在分叉的第一激波的前缘斜激波处，边界层厚度增加，而在尾激波处，边界层厚度减小;在低边界条件下，分叉的第一激波下方边界层分离，而在高边界条件下，边界层分离。其次，利用激光多普勒测速仪（LDV）对MSW-TBLI内的时均速度和脉动速度进行了详细的测量。雷诺剪应力和湍流动能。结果表明，湍流强度。在分叉激波作用下，MSW-TBLI边界层中的雷诺剪应力和湍流动能增加